CA2035407A1 - Hover position hold system for rotary winged aircraft - Google Patents

Hover position hold system for rotary winged aircraft

Info

Publication number
CA2035407A1
CA2035407A1 CA2035407A CA2035407A CA2035407A1 CA 2035407 A1 CA2035407 A1 CA 2035407A1 CA 2035407 A CA2035407 A CA 2035407A CA 2035407 A CA2035407 A CA 2035407A CA 2035407 A1 CA2035407 A1 CA 2035407A1
Authority
CA
Canada
Prior art keywords
signal
complementary
utilized
referenced
transformed
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
CA2035407A
Other languages
French (fr)
Other versions
CA2035407C (en
Inventor
Phillip Jeremy Gold
Joseph Apostolato Post
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
RTX Corp
Original Assignee
United Technologies Corp
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by United Technologies Corp filed Critical United Technologies Corp
Publication of CA2035407A1 publication Critical patent/CA2035407A1/en
Application granted granted Critical
Publication of CA2035407C publication Critical patent/CA2035407C/en
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

Links

Classifications

    • G—PHYSICS
    • G05—CONTROLLING; REGULATING
    • G05D—SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES
    • G05D1/00—Control of position, course, altitude or attitude of land, water, air or space vehicles, e.g. using automatic pilots
    • G05D1/08—Control of attitude, i.e. control of roll, pitch, or yaw
    • G05D1/0808—Control of attitude, i.e. control of roll, pitch, or yaw specially adapted for aircraft
    • G05D1/0858—Control of attitude, i.e. control of roll, pitch, or yaw specially adapted for aircraft specially adapted for vertical take-off of aircraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/54—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement
    • B64C27/56—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement characterised by the control initiating means, e.g. manually actuated
    • B64C27/57—Mechanisms for controlling blade adjustment or movement relative to rotor head, e.g. lag-lead movement characterised by the control initiating means, e.g. manually actuated automatic or condition responsive, e.g. responsive to rotor speed, torque or thrust

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Automation & Control Theory (AREA)
  • Mechanical Engineering (AREA)
  • Navigation (AREA)
  • Control Of Position, Course, Altitude, Or Attitude Of Moving Bodies (AREA)
  • Position Fixing By Use Of Radio Waves (AREA)

Abstract

A ground-plane-referenced, acceleration signal (2) and Doppler velocity signal (56) are utilized by a complementary filter (6) to provide a complementary velocity signal (8) which is transformed (60) to an inertial coordinate referenced velocity signal (62) utilized in combination with a GPS position signal (56) by a complementary filter (68) to provide a complementary, position error signal (130) that is transformed to a ground-plane-referenced, position error signal (168) and summed with a wind speed signal (196) calculated from the difference between air speed (200) and the aforementioned complementary velocity signal (8) to provide a pitch command signal (202). A similar system is utilized to provide a roll command signal. The system is gated by signals (100, 176) which are determinative of the aircraft meeting predetermined flight conditions (250-262).
CA002035407A 1990-05-03 1991-01-31 Hover position hold system for rotary winged aircraft Expired - Fee Related CA2035407C (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US518,593 1990-05-03
US07/518,593 US5195039A (en) 1990-05-03 1990-05-03 Hover position hold system for rotary winged aircraft

Publications (2)

Publication Number Publication Date
CA2035407A1 true CA2035407A1 (en) 1991-11-04
CA2035407C CA2035407C (en) 1996-11-12

Family

ID=24064618

Family Applications (1)

Application Number Title Priority Date Filing Date
CA002035407A Expired - Fee Related CA2035407C (en) 1990-05-03 1991-01-31 Hover position hold system for rotary winged aircraft

Country Status (5)

Country Link
US (2) US5195039A (en)
EP (1) EP0455580B1 (en)
JP (1) JP2911638B2 (en)
CA (1) CA2035407C (en)
DE (2) DE69107235T2 (en)

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US5841370A (en) * 1996-09-20 1998-11-24 Lempicke; Thomas A. Method and apparatus for determining aircraft bank angle using satellite navigational signals
US6076024A (en) * 1998-04-29 2000-06-13 Sikorsky Aircraft Corporation Earth-referenced wind adjustment for hovering aircraft
FR2787587B1 (en) * 1998-12-18 2001-10-05 Sextant Avionique PROCESS FOR THE REAL-TIME DEVELOPMENT OF TRAJECTORIES FOR AN AIRCRAFT
US6236914B1 (en) 1999-06-16 2001-05-22 Lockheed Martin Corporation Stall and recovery control system
US6246929B1 (en) 1999-06-16 2001-06-12 Lockheed Martin Corporation Enhanced stall and recovery control system
US6648269B2 (en) 2001-12-10 2003-11-18 Sikorsky Aircraft Corporation Trim augmentation system for a rotary wing aircraft
JP4130598B2 (en) * 2003-03-07 2008-08-06 ヤマハ発動機株式会社 GPS control method for unmanned helicopter
US6731234B1 (en) 2003-06-11 2004-05-04 Honeywell International Inc. Radar anti-fade systems and methods
US7248208B2 (en) * 2004-06-10 2007-07-24 Honeywell International Inc. Methods and systems for maintaining a position during hovering operations
US7100866B2 (en) * 2005-01-14 2006-09-05 Rehco, Llc Control system for a flying vehicle
FR2882163B1 (en) * 2005-02-15 2011-05-27 Thales Sa AUTOMATIC DRIVING EQUIPMENT FOR ROTARY TURNING AIRCRAFT
FR2897956B1 (en) * 2006-02-28 2008-04-04 Airbus France Sas METHOD AND DEVICE FOR ASSISTING A PILOT OF A FOLLOWING AIRCRAFT ON A PATROL FLIGHT
US20080077284A1 (en) * 2006-04-19 2008-03-27 Swope John M System for position and velocity sense of an aircraft
FR2914074B1 (en) * 2007-03-23 2014-10-31 Thales Sa METHOD FOR GENERATING VALUES OF INSTRUCTIONS FOR SERVING A PARAMETER OF FLIGHT P OF AN AIRCRAFT EQUIPPED WITH AN AUTOMATIC PILOT.
US8694182B2 (en) * 2007-04-03 2014-04-08 Sikorsky Aircraft Corporation Altitude and acceleration command altitude hold algorithm for rotorcraft with large center of gravity range
US8442706B2 (en) * 2008-12-30 2013-05-14 Sikorsky Aircraft Corporation Module for integrated approach to an offshore facility
EP2261116B1 (en) * 2009-06-09 2019-05-22 Sikorsky Aircraft Corporation Automatic trim system for fly-by-wire aircraft with unique trim controllers
US8712607B2 (en) * 2009-12-07 2014-04-29 Sikorsky Aircraft Corporation Systems and methods for velocity profile based approach to point control
US8648607B2 (en) * 2010-01-05 2014-02-11 Amperic, Inc. Monitoring power usage
WO2012096668A1 (en) 2011-01-14 2012-07-19 Bell Helicopter Textron Inc. Flight control laws for vertical flight path control
FR2989795B1 (en) * 2012-04-24 2015-02-06 Thales Sa PARAMETRAL AUTOMATIC DRIVING SYSTEM FOR AN AIRCRAFT
US8639400B1 (en) 2012-09-26 2014-01-28 Silverlit Limited Altitude control of an indoor flying toy
US9108612B2 (en) * 2013-04-22 2015-08-18 John Gregory Hovercraft with multiple, independently-operable lift chambers
US9360869B1 (en) 2013-12-03 2016-06-07 Sikorsky Aircraft Corporation Vehicle heading error compensation
FR3023018B1 (en) 2014-06-30 2016-06-10 Airbus Helicopters METHOD AND SYSTEM FOR THE STATIONARY FLYING OF AN AIRCRAFT WITH A ROTATING SAILING SYSTEM WHILE TAKING A TRAJECTORY OR HOLDING A CAP, ACCORDING TO ITS SPEED OF PROGRESS
FR3023016B1 (en) 2014-06-30 2016-07-01 Airbus Helicopters SYSTEM AND METHOD FOR FLIGHT CONTROL IN TRAJECTORY FOR A ROTARY WING AIRCRAFT
FR3023017B1 (en) * 2014-06-30 2016-06-10 Airbus Helicopters SYSTEM AND METHOD FOR FLIGHT CONTROL OF AN AIRCRAFT WITH A ROTATING SAILING SYSTEM WHILE TAKING A TRAJECTORY OR HOLDING A CAP, ACCORDING TO ITS SPEED OF PROGRESS
WO2016178738A1 (en) * 2015-05-05 2016-11-10 Sikorsky Aircraft Corporation Position hold override control
US10040542B1 (en) * 2017-02-07 2018-08-07 Bell Helicopter Textron Inc. System and method for stabilizing longitudinal acceleration of a rotorcraft
US10386843B2 (en) * 2017-04-03 2019-08-20 Bell Helicopter Textron Inc. System and method for determining a position of a rotorcraft
US10611463B2 (en) * 2017-04-05 2020-04-07 Textron Innovations Inc. Rotorcraft fly-by-wire stabilization
US10816971B2 (en) * 2018-02-12 2020-10-27 Textron Innovations Inc. Autopilot recoupling for rotorcraft
US10890668B2 (en) * 2018-06-28 2021-01-12 Textron Innovations Inc. System and method for determining a velocity of a rotorcraft

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Also Published As

Publication number Publication date
US5301112A (en) 1994-04-05
EP0455580B1 (en) 1995-02-08
CA2035407C (en) 1996-11-12
DE455580T1 (en) 1992-02-27
EP0455580A3 (en) 1992-02-26
JP2911638B2 (en) 1999-06-23
JPH0789493A (en) 1995-04-04
DE69107235D1 (en) 1995-03-23
US5195039A (en) 1993-03-16
EP0455580A2 (en) 1991-11-06
DE69107235T2 (en) 1995-05-24

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